Overhead payload module with integrated stowbins

ABSTRACT

In an example, an overhead payload module is described. The overhead payload module comprises a ceiling assembly, an aisle floor assembly, a first payload assembly attached to the ceiling assembly and the aisle floor assembly to form a first side of the overhead payload module, and a second payload assembly attached to the ceiling assembly and the aisle floor assembly to form a second side of the overhead payload module. The first payload assembly comprises a first payload module and a first overhead stowbin module structurally integrated with the first payload module and having a first stowage area configured to receive stowbins. The second payload assembly is positioned opposite the first payload assembly to form an aisle therebetween and comprises a second payload module and a second overhead stowbin module structurally integrated with the second payload module and having a second stowage area configured to receive stowbins.

CROSS REFERENCE TO RELATED APPLICATION

The present disclosure is a continuation of U.S. patent application Ser.No. 16/134,685, filed on Sep. 18, 2018, the entire contents of which areherein incorporated by reference.

FIELD

The present disclosure relates generally to an overhead payload modulein an aircraft, and more particularly, to a module that can bestructurally integrated with stowbins and installed in the aircraft.

BACKGROUND

Certain types of aircrafts, such as those used for flights that occurovernight and/or flights that are longer in duration, often includemodules for accommodation of crew members. Some such modules can bepositioned above or below the main cabin area of the aircraft and caninclude an aisleway or other means of movement through the module.

In existing aircrafts where such a module is positioned above the maincabin area, the module is typically positioned above the main cabinstowbins that are used by passengers. In particular, the module istypically mounted within the aircraft to a support structure. A stowbinsupport assembly in which the stowbins can be inserted is alsoseparately mounted to the support structure underneath the module suchthat the module is independent of the stowbin support assembly. Thisstowbin support assembly also typically serves as an integrationplatform for various systems within the aircraft, such as air systems,lighting, etc.

Modules and stowbin support assemblies in existing arrangements oftenhave space that is unutilized or underutilized. As another example,existing arrangements are heavier than desired, and both costly tomanufacture and install. For instance, because the module and thestowbin support assembly are typically mounted within the aircraft tothe same support structure, the support structure typically requiresspace for both commodities. In addition, having to separately mount andsecure the module and the stowbin support assembly to the same supportstructure can increase the amount of time spent during installation andcan require excessive components such as fasteners.

SUMMARY

In an example, an overhead payload module for installation in anaircraft is described. The overhead payload module comprises a ceilingassembly, an aisle floor assembly, a first payload assembly, a secondpayload assembly, and a plurality of aisle support structures. The firstpayload assembly is attached to the ceiling assembly and the aisle floorassembly to form a first side of the overhead payload module andcomprises a first payload module comprising a first floor panel, and afirst overhead stowbin module structurally integrated with the firstpayload module and having a first stowage area configured to receivestowbins and accessible via a main cabin area of the aircraft. The firstoverhead stowbin module comprises a first pair of end walls attached toa first stowbin side wall, and the first pair of end walls, the firststowbin side wall, and the first floor panel define the first stowagearea. The second payload assembly is attached to the ceiling assemblyand the aisle floor assembly to form a second side of the overheadpayload module. The second payload assembly is positioned opposite thefirst payload assembly to form an aisle therebetween and comprises asecond payload module comprising a second floor panel, and a secondoverhead stowbin module structurally integrated with the second payloadmodule and having a second stowage area configured to receive stowbinsand accessible via the main cabin area of the aircraft. The secondoverhead stowbin module comprises a second pair of end walls attached toa second stowbin side wall, and the second pair of end walls, the secondstowbin side wall, and the second floor panel define the second stowagearea. The plurality of aisle support structures is attached to theoverhead payload module at a plurality of different locations along alength of the aisle floor assembly. Each aisle support structure of theplurality of aisle support structures comprises a first support brackethaving a first arm attached to the first payload assembly and a secondarm attached to the aisle floor assembly, a second support bracketpositioned opposite the first support bracket and having a first armattached to the second payload assembly and a second arm attached to theaisle floor assembly, and a cross member having a first end portionattached between the aisle floor assembly and the first support bracketand having a second end portion attached between the aisle floorassembly and the second support bracket.

In another example, an aircraft is described comprising a fuselage, anoverhead payload module, and a support rail assembly positioned withinthe fuselage and configured to support the overhead payload module. Theoverhead payload module comprises a ceiling assembly, an aisle floorassembly positioned above the main cabin area of the aircraft, a firstpayload assembly, a second payload assembly, and a plurality of aislesupport structures. The first payload assembly is attached to theceiling assembly and the aisle floor assembly to form a first side ofthe overhead payload module and comprises a first payload modulecomprising a first floor panel, and a first overhead stowbin modulestructurally integrated with the first payload module and having a firststowage area configured to receive stowbins and accessible via the maincabin area of the aircraft. The first overhead stowbin module comprisesa first pair of end walls attached to a first stowbin side wall, and thefirst pair of end walls, the first stowbin side wall, and the firstfloor panel define the first stowage area. The second payload assemblyis attached to the ceiling assembly and the aisle floor assembly to forma second side of the overhead payload module. The second payloadassembly is positioned opposite the first payload assembly to form anaisle therebetween and comprises a second payload module comprising asecond floor panel, and a second overhead stowbin module structurallyintegrated with the second payload module and having a second stowagearea configured to receive stowbins and accessible via the main cabinarea of the aircraft. The second overhead stowbin module comprises asecond pair of end walls attached to a second stowbin side wall, and thesecond pair of end walls, the second stowbin side wall, and the secondfloor panel define the second stowage area. The plurality of aislesupport structures is attached to the overhead payload module at aplurality of different locations along a length of the aisle floorassembly. Each aisle support structure of the plurality of aisle supportstructures comprises a first support bracket having a first arm attachedto the first payload assembly and a second arm attached to the aislefloor assembly, a second support bracket positioned opposite the firstsupport bracket and having a first arm attached to the second payloadassembly and a second arm attached to the aisle floor assembly, and across member having a first end portion attached between the aisle floorassembly and the first support bracket and having a second end portionattached between the aisle floor assembly and the second supportbracket.

In another example, a method for balancing load in, and reinforcing anaisle structure of, an overhead payload module of an aircraft isdescribed. The method comprises attaching a first payload assembly to(i) a ceiling assembly and (ii) an aisle floor assembly to form a firstside of the overhead payload module. The first payload assemblycomprises a first payload module comprising a first floor panel, and afirst overhead stowbin module structurally integrated with the firstpayload module and having a first stowage area configured to receivestowbins and accessible via a main cabin area of the aircraft. The firstoverhead stowbin module comprises a first pair of end walls attached toa first stowbin side wall, and the first pair of end walls, the firststowbin side wall, and the first floor panel define the first stowagearea. The method further comprises attaching a second payload assemblyto (i) the ceiling assembly and (ii) the aisle floor assembly to form asecond side of the overhead payload module, wherein the second payloadassembly is positioned opposite the first payload assembly to form anaisle therebetween. The second payload assembly comprises a secondpayload module comprising a second floor panel, and a second overheadstowbin module structurally integrated with the second payload moduleand having a second stowage area configured to receive stowbins andaccessible via the main cabin area of the aircraft. The second overheadstowbin module comprises a second pair of end walls attached to a secondstowbin side wall, and the second pair of end walls, the second stowbinside wall, and the second floor panel define the second stowage area.The method further comprises attaching a plurality of aisle supportstructures to the overhead payload module at a plurality of differentlocations along a length of the aisle floor assembly, where attachingthe plurality of aisle support structures to the overhead payload modulecomprises, for each aisle support structure of the plurality of aislesupport structures: attaching a first arm of a first support bracket tothe first payload assembly and a second arm of the first support bracketto the aisle floor assembly, attaching a first arm of a second supportbracket, positioned opposite the first support bracket, to the secondpayload assembly and a second arm of the second support bracket to theaisle floor assembly, and attaching a first end portion of a crossmember between the aisle floor assembly and the first support bracketand a second end portion of the cross member between the aisle floorassembly and the second support bracket.

In another example, an overhead payload module for installation in anaircraft is described. The overhead payload module comprises a ceilingassembly, an aisle floor assembly, a first payload assembly, and asecond payload assembly. The first payload assembly is attached to theceiling assembly and the aisle floor assembly to form a first side ofthe overhead payload module. The first payload assembly comprises afirst payload module comprising a first floor panel and a first backwall, a first plurality of blade fittings attached along a length of anexterior of the first payload module to the first back wall and thefirst floor panel, and a first overhead stowbin module structurallyintegrated with the first payload module and having a first stowage areaconfigured to receive stowbins and accessible via a main cabin area ofthe aircraft. The second payload assembly is attached to the ceilingassembly and the aisle floor assembly to form a second side of theoverhead payload module and is positioned opposite the first payloadassembly to form an aisle therebetween. The second payload assemblycomprises a second payload module comprising a second floor panel and asecond back wall, a second plurality of blade fittings attached along alength of an exterior of the second payload module to the second backwall and the second floor panel, and a second overhead stowbin modulestructurally integrated with the second payload module and having asecond stowage area configured to receive stowbins and accessible viathe main cabin area of the aircraft. Each blade fitting of the firstplurality of blade fittings and the second plurality of blade fittingsis configured for attaching to a support rail assembly of the aircraftso as to attach the overhead payload module to the support rail assemblywithin the aircraft.

In another example, an aircraft is described comprising a fuselage, anoverhead payload module, and a support rail assembly a support railassembly positioned within the fuselage and configured to support theoverhead payload module. The overhead payload module comprises a ceilingassembly, an aisle floor assembly positioned above a main cabin area ofthe aircraft, a first payload assembly, and a second payload assembly.The first payload assembly is attached to the ceiling assembly and theaisle floor assembly to form a first side of the overhead payloadmodule. The first payload assembly comprises a first payload modulecomprising a first floor panel and a first back wall, a first pluralityof blade fittings attached along a length of an exterior of the firstpayload module to the first back wall and the first floor panel, and afirst overhead stowbin module structurally integrated with the firstpayload module and having a first stowage area configured to receivestowbins and accessible via the main cabin area of the aircraft. Thesecond payload assembly is attached to the ceiling assembly and theaisle floor assembly to form a second side of the overhead payloadmodule and is positioned opposite the first payload assembly to form anaisle therebetween. The second payload assembly comprises a secondpayload module comprising a second floor panel and a second back wall, asecond plurality of blade fittings attached along a length of anexterior of the second payload module to the second back wall and thesecond floor panel, and a second overhead stowbin module structurallyintegrated with the second payload module and having a second stowagearea configured to receive stowbins and accessible via the main cabinarea of the aircraft. Each blade fitting of the first plurality of bladefittings and the second plurality of blade fittings is configured forattaching to a support rail assembly of the aircraft so as to attach theoverhead payload module to the support rail assembly within theaircraft. Each blade fitting of the first plurality of blade fittingsand the second plurality of blade fittings is configured for attachingto the support rail assembly so as to attach the overhead payload moduleto the support rail assembly within the aircraft.

In another example, a method for or assembling an overhead payloadmodule of an aircraft is described. The method comprises attaching afirst payload assembly to (i) a ceiling assembly and (ii) an aisle floorassembly to form a first side of the overhead payload module. The firstpayload assembly comprises a first payload module comprising a firstfloor panel and a first back wall, and a first overhead stowbin modulestructurally integrated with the first payload module and having a firststowage area configured to receive stowbins and accessible via a maincabin area of the aircraft. The method further comprises attaching asecond payload assembly to (i) the ceiling assembly and (ii) the aislefloor assembly to form a second side of the overhead payload module,where the second payload assembly is positioned opposite the firstpayload assembly to form an aisle therebetween. The second payloadassembly comprises a second payload module comprising a second floorpanel and a second back wall, and a second overhead stowbin modulestructurally integrated with the second payload module and having asecond stowage area configured to receive stowbins and accessible viathe main cabin area of the aircraft. The method further comprisesattaching a first plurality of blade fittings along a length of anexterior of the first payload module to the first back wall and thefirst floor panel and attaching a second plurality of blade fittingsalong a length of an exterior of the second payload module to the secondback wall and the second floor panel. Each blade fitting of the firstplurality of blade fittings and the second plurality of blade fittingsis configured for attaching to a support rail assembly of the aircraftso as to attach the overhead payload module to the support rail assemblywithin the aircraft.

In another example, a method for installing an overhead payload modulein an aircraft is described. The method comprises providing a supportrail assembly in the aircraft, where the support rail assembly comprisesa first support rail positioned on a first side of the aircraft and asecond support rail positioned on a second side of the aircraft oppositethe first side, where the first support rail and the second support railare substantially parallel and substantially planar. The method furthercomprises attaching the overhead payload module to the support railassembly to position the overhead payload module above a main cabin areaof the aircraft and between the first support rail and the secondsupport rail. The overhead payload module comprises a first payloadassembly and a second payload assembly. The first payload assemblycomprises a first payload module, a first overhead stowbin modulestructurally integrated with the first payload module and having a firststowage area, and a first plurality of blade fittings attached along alength of an exterior of the first payload module. Each blade fitting ofthe first plurality of blade fittings comprises a bracket portionattached to a first back wall and a first floor panel of the firstpayload module and a hook portion protruding from the bracket portionand attachable to the first support rail. The second payload assemblycomprises a second payload module, a second overhead stowbin modulestructurally integrated with the second payload module and having asecond stowage area, and a second plurality of blade fittings attachedalong a length of an exterior of the second payload module. Each bladefitting of the second plurality of blade fittings comprises a bracketportion attached to a second back wall and a second floor panel of thesecond payload module and a hook portion protruding from the bracketportion and attachable to the second support rail. Attaching theoverhead payload module to the support rail assembly to position theoverhead payload module above the main cabin area of the aircraft andbetween the first support rail and the second support rail comprisesattaching the hook portion of each blade fitting of the first pluralityof blade fittings to the first support rail and attaching the hookportion of each blade fitting of the second plurality of blade fittingsto the second support rail.

The features, functions, and advantages that have been discussed can beachieved independently in various examples or may be combined in yetother examples. Further details of the examples can be seen withreference to the following description and drawings.

BRIEF DESCRIPTION OF THE FIGURES

The novel features believed characteristic of the illustrative examplesare set forth in the appended claims. The illustrative examples,however, as well as a preferred mode of use, further objectives anddescriptions thereof, will best be understood by reference to thefollowing detailed description of an illustrative example of the presentdisclosure when read in conjunction with the accompanying drawings,wherein:

FIG. 1 is a perspective view of an aircraft, according to an exampleimplementation.

FIG. 2 is a front view of an overhead payload module, according to anexample implementation.

FIG. 3 is a front view of a cross-section of the aircraft where theoverhead payload module is positioned in a fuselage of the aircraft,according to an example implementation.

FIG. 4 is an exploded view of the overhead payload module, according toan example implementation.

FIG. 5 is an exploded view of a first payload assembly of the overheadpayload module, according to an example implementation.

FIG. 6 is an exploded view of a second payload assembly of the overheadpayload module, according to an example implementation.

FIG. 7 is a perspective view of a passenger service unit (PSU) supportassembly attachable to an aisle floor assembly of the overhead payloadmodule, according to an example implementation.

FIG. 8 is a front view of the PSU support assembly housing a PSU,according to an example implementation.

FIG. 9 is a perspective view of a plurality of aisle support structuresattached along a length of the aisle floor assembly, according to anexample implementation.

FIG. 10 is a perspective view of the plurality of aisle supportstructures attached to the overhead payload module along a length of theaisle floor assembly, according to an example implementation.

FIG. 11 is a perspective view of a representative support bracket of anaisle support structure of the plurality of aisle support structures,according to an example implementation.

FIG. 12 is another perspective view of the aisle support structure,according to an example implementation.

FIG. 13 is a perspective view of the overhead payload module including afirst plurality of blade fittings, according to an exampleimplementation.

FIG. 14 is another perspective view of the overhead payload moduleincluding a second plurality of blade fittings, according to an exampleimplementation.

FIG. 15 is a perspective view of the overhead payload module attached toa support rail assembly, according to an example implementation.

FIG. 16 is a side view of a blade fitting, according to an exampleimplementation.

FIG. 17 illustrates a perspective view of the blade fitting and asupport rail, as well as another side view of the blade fitting,according to an example implementation.

FIG. 18 depicts an arrangement of blade fittings of the overhead payloadmodule used to attach the overhead payload module to the support railassembly, according to an example implementation.

FIG. 19 is a perspective view of another type of blade fitting,according to an example implementation.

FIG. 20 shows a flowchart of an example method for balancing load in,and reinforcing an aisle structure of, the overhead payload module ofthe aircraft, according to an example implementation.

FIG. 21 shows a flowchart of an example method for use with the methodof FIG. 20, according to an example implementation.

FIG. 22 shows a flowchart of an example method for performing one of theattaching functions of the method of FIG. 20, according to an exampleimplementation.

FIG. 23 shows a flowchart of another example method for use with themethod of FIG. 20, according to an example implementation.

FIG. 24 shows a flowchart of another example method for use with themethod of FIG. 20, according to an example implementation.

FIG. 25 shows a flowchart of an example method for assembling theoverhead payload module of the aircraft, according to an exampleimplementation.

FIG. 26 shows a flowchart of an example method for performing two of theattaching functions of the method of FIG. 25, according to an exampleimplementation.

FIG. 27 shows a flowchart of another example method for performing twoof the attaching functions of the method of FIG. 25, according to anexample implementation.

FIG. 28 shows a flowchart of an example method for use with the methodof FIG. 25, as well as a flowchart of another example method forperforming two of the attaching functions of the method of FIG. 25,according to an example implementation.

FIG. 29 shows a flowchart of an example method for installing theoverhead payload module in the aircraft, according to an exampleimplementation.

FIG. 30 shows a flowchart of an example method for performing theattaching function of the method of FIG. 29, according to an exampleimplementation.

FIG. 31 shows a flowchart of an example method for performing theattaching functions of the method of FIG. 30, according to an exampleimplementation.

DETAILED DESCRIPTION

Disclosed examples will now be described more fully hereinafter withreference to the accompanying drawings, in which some, but not all ofthe disclosed examples are shown. Indeed, several different examples maybe described and should not be construed as limited to the examples setforth herein. Rather, these examples are described so that thisdisclosure will be thorough and complete and will fully convey the scopeof the disclosure to those skilled in the art.

Within examples, an overhead payload module is described. Morespecifically, example systems describe the overhead payload modulewithin an aircraft, and example methods describe assembling the overheadpayload module, installing the overhead payload module in the aircraft,and configuring the overhead payload module to balance load andreinforce an aisle structure of the overhead payload module.

The term “overhead payload module,” as used herein, describes astructure that integrates a payload structure (which defines a payloadarea) with an overhead stowbin module. By way of example, such a payloadstructure and corresponding area can take the form of a crew rest orpassenger rest area that includes bunks, tables, and/or othercommodities. As another example, such a payload structure andcorresponding area could take the form of a stowage area for luggageand/or other objects, or perhaps another area in which crew and/orpassengers could be seated, as an alternative to the main cabin seating.Other payload examples are possible as well.

The methods and systems described herein may involve an overhead payloadmodule having two sides, each having a respective payload module thatstructurally integrates a stowbin module. This structural integrationcan cause the overhead payload module to be more ergonomic, less costly,less heavy, and easier to assemble and install than existingarrangements. Other advantages are described herein as well.

What is needed is an overhead module that is stronger and more ergonomicand structurally efficient, which can in turn reduce cost and time spentduring manufacture and installation, and can provide improved loadcarrying capabilities.

To structurally reinforce the overhead payload module and enable theoverhead payload module to carry loads in a desirable manner, theoverhead payload module includes various aisle support structures thatattach to an aisle floor assembly of the overhead payload module, aswell as to various other components of the overhead payload module.These aisle support structures help create, in effect, a load path fromone side of the overhead payload module to the other, and can helpincrease the load-carrying capabilities of the overhead payload module.Further, these aisle support structures, as well as other componentsdescribed herein, can improve the strength and stability of the aisle ofthe overhead payload module. For example, the stowbin modules includevarious walls that define a stowage area into which stowbins can beinserted. Some of these walls can serve as vertical support means thatare attached to, contacting, or otherwise structurally reinforcing theaisle. The overhead payload module can be configured in other ways aswell to structurally reinforce the overhead payload module and enablethe overhead payload module to carry loads in a desirable manner.

Additionally or alternatively, to secure the overhead payload module tosupport rails when the overhead payload module is installed in theaircraft, the overhead payload module includes various “blade fittings”that are configured in such a way that enables the overhead payloadmodule to be more easily secured to the support rails duringinstallation. In addition, these blade fittings can help stabilize theoverhead payload module within the aircraft and increase the ability ofthe overhead payload module to handle loads. For example, the bladefittings can be arranged and configured such that one or more bladefittings include spherical bearings for attaching the blade fitting(s)to the support rails and one or more other blade fittings include anon-spherical bearing for attaching the other blade fitting(s) to thesupport rails. Because the spherical bearings have more freedom ofmovement than non-spherical bearings, the blade fittings havingspherical bearings can compensate for excessive loads and any potentialmisalignment. As such, the blade fittings having spherical bearings andthe blade fittings having non-spherical bearings can be arranged in amanner that designates a desirable load path through areas of theoverhead payload module that can handle such loads more easily thanother areas, thereby improving load distribution.

These and other improvements are described in more detail below.Implementations described below are for purposes of example. Theimplementations described below, as well as other implementations, mayprovide other improvements as well.

Referring now to the figures, FIG. 1 is a perspective view of anaircraft 100, according to an example implementation. Aircraft 100includes a fuselage 102 that can include a main cabin area, an overheadpayload module, and other components and areas of the aircraft 100.

FIG. 2 is a front view of an overhead payload module 104, according toan example implementation. As shown, the overhead payload module 104includes a ceiling assembly 106, an aisle floor assembly 108, a firstpayload assembly 110, and a second payload assembly 112.

As shown, the first payload assembly 110 is attached to the ceilingassembly 106 and the aisle floor assembly 108 on one side of the ceilingassembly 106 and the aisle floor assembly 108, thus forming a first sideof the overhead payload module 104. Further, the second payload assembly112 is attached to the ceiling assembly 106 and the aisle floor assembly108 on the opposite side of the ceiling assembly 106 and the aisle floorassembly 108, thus forming a second side of the overhead payload module104. In addition, the positioning of the first payload assembly 110 andthe second payload assembly 112 opposite each other forms an aisle 113between the first payload assembly 110 and the second payload assembly112. Any two or more of these assembles could be attached by way of oneor more fasteners or by other means.

The first payload assembly 110 and the second payload assembly 112 eachincludes a respective payload module and a respective overhead stowbinmodule, which are designated by brackets in FIG. 2. In particular, thefirst payload assembly 110 includes a first payload module 114 and afirst overhead stowbin module 116. The first overhead stowbin module 116may define a first stowage area that is configured to receive stowbinsand that is accessible via a main cabin area of the aircraft 100 (e.g.,main cabin area 121 shown in FIG. 3). As an example, FIG. 2 shows arepresentative stowbin 117 installed in the first overhead stowbinmodule 116. Further, the second payload assembly 112 includes a secondpayload module 118 and a second overhead stowbin module 120. The secondoverhead stowbin module 116 may define a second stowage area that isconfigured to receive stowbins and that is accessible via a main cabinarea of the aircraft 100. As an example, FIG. 2 shows a representativestowbin 117 installed in the second overhead stowbin module 120.Although not shown in FIG. 2, more stowbins can be installed in eachoverhead stowbin module.

As shown, the first overhead stowbin module 116 is structurallyintegrated with the first payload module 114, and the second overheadstowbin module 120 is structurally integrated with the second payloadmodule 118.

Various components of the overhead payload module 104 described hereincould be structurally integrated. In some examples, structurallyintegrated means that the payload modules 114, 118 and the overheadstowbin modules 116, 120 are attached prior to installation into theaircraft 100 so that the overhead payload module 104 can be installed inthe aircraft 100 as a single component or piece. Additionally oralternatively, structurally integrated means that the first payloadmodule 114 is manufactured as one integral component and the firstoverhead stowbin module 116 is manufactured as one integral component,and the two components are attached (e.g., bolted) together prior toinstallation in the aircraft 100, and likewise, the second payloadmodule 118 is manufactured as one integral component and the secondoverhead stowbin module 120 is manufactured as one integral component,and the two components are attached together prior to installation inthe aircraft 100. Additionally or alternatively, structurally integratedmeans that at least one component of the first payload module 114 isintegrally formed with at least one component of the first overheadstowbin module 116 as a single contiguous component, and likewise, atleast one component of the second payload module 116 is integrallyformed with at least one component of the second overhead stowbin module120 as a single contiguous component. By way of example, as will bediscussed in more detail below, a side wall of a payload module could beintegrally formed with an end wall of an overhead stowbin module.Additionally or alternatively, structurally integrated means that atleast one component that forms the first payload module 114 could alsobe a component that forms the first overhead stowbin module 116, andlikewise, at least one component that forms the second payload module118 could also be a component that forms the second overhead stowbinmodule 120. For example, a floor panel of a payload module could alsoserve as a ceiling of an overhead stowbin module, and thus the payloadmodule and overhead stowbin module share the floor panel component.Other examples are possible as well.

Having the overhead stowbin modules structurally integrated with thepayload modules can minimize the amount of structures in the aircraft100, eliminate redundancies in components, reduce the weight of theoverhead payload module 104, and make the overhead payload module 104less costly and more efficient to manufacture. Further, this integrationcan reduce the time and manual work spent installing the overheadpayload module 104, in part because one single structure—namely, theoverhead payload module 104—need be mounted within the aircraft 100.Other advantages are possible as well.

Moreover, the structural integration of the overhead stowbin moduleswith the payload modules can further increase structural efficiency byenabling various commodities of the aircraft 100 to be integrated withthe overhead payload module 104. For example, main cabin ceilings,lighting, ducts, wiring, and/or other miscellaneous components can becarried by the overhead payload module 104.

FIG. 3 is a front view of a cross-section of the aircraft 100 where theoverhead payload module 104 is positioned in the fuselage 102 of theaircraft 100, according to an example implementation. As shown, theaircraft 100 includes a main cabin area 121 and the overhead payloadmodule 104 is poisoned in the aircraft 100 above the main cabin area121. More particularly, the overhead payload module 104 is positionedsuch that the ceiling assembly 106 is positioned proximate to aninterior surface of the fuselage 102 (e.g., the surface of the fuselage102 that is facing the interior of the aircraft 100). For example, theoverhead payload module 104 may be positioned such that itabutting/contacting the interior surface of the fuselage 102, or suchthat it is within a threshold distance (e.g., 25.4 millimeters) from theinterior surface of the fuselage 102. The ceiling assembly 106 could bepositioned such that it is either directly adjacent to the fuselage 102or positioned with other materials in between the ceiling assembly 106and the fuselage 102. Further, the overhead payload module 104 ispositioned such that the aisle floor assembly 108 is directly, or almostdirectly, above the main cabin area 121. With the overhead payloadmodule 104 positioned in the manner shown in FIG. 3, stowbins that areinserted into the overhead payload module 104 can be accessed via themain cabin area 121.

The overhead payload module 104 can be secured within the aircraft 100above the main cabin area 121 of the aircraft 100, and can be secured invarious ways, such as being secured to a support rail assembly or othersupport structure. A support rail assembly is not shown in FIG. 3, butis described in more detail in later Figures.

FIG. 4 is an exploded view of the overhead payload module 104, accordingto an example implementation. The exploded view of the overhead payloadmodule 104 shows the ceiling assembly 106, the aisle floor assembly 108,the first payload assembly 110, and the second payload assembly 112 asseparate components. It should be understood that two or more of theseassemblies could be manufactured such that they are integrally formedrather than being separate components that are assembled together toform the overhead payload module 104.

FIG. 5 is an exploded view of the first payload assembly 110 of theoverhead payload module 104, according to an example implementation. Asshown, the first payload assembly 110 comprises a first floor panel 122,a first back wall 124, a first ceiling 126, a first pair of side walls128, 130 that together form the first payload module 114 portion of thefirst payload assembly 110. Further, the first payload assembly 110comprises a first pair of end walls 132, 134 and a first stowbin sidewall 136 that together form the first overhead stowbin module 116. Inaddition, the first pair of end walls 132, 134, the first stowbin sidewall 136, and the first floor panel 122 together define a first stowagearea underneath the first floor panel 122 configured to receive stowbinsand accessible via the main cabin area 121 of the aircraft 100. Inaddition to or alternative to the components shown in FIG. 5, the firstpayload assembly 110 can include other walls or other structures,depending on the type of payload area defined. For instance, the firstpayload module 114 may include other walls that enclose a crew restspace.

As shown, one side wall 128 of the first pair of side walls 128, 130 isintegrally formed with one end wall 132 of the first pair of end walls132, 134. And the other side wall 130 of the first pair of side walls128, 130 is integrally formed with the other end wall 134 of the firstpair of end walls 132, 134. Having this type of integral formation canprovide increased structural integrity to the first payload assembly 110and the aisle area of the overhead payload module 104, such as byreinforcing the first stowbin side wall 136, and possibly in turn theaisle floor assembly 108. However, in alternative implementations, theside walls of the first pair of side walls 128, 130 may be independentfrom the end walls of the first pair of end walls 132, 134, and thusindependently attached when assembling the first payload assembly 110.

Further, as shown in FIG. 5, a first plurality of supplemental brackets,including representative supplemental bracket 137, are attached to thefirst stowbin side wall 136. Each supplemental bracket of the firstplurality of supplemental brackets has a first arm attached to the firststowbin side wall 136 and a second arm that can be attached to the aislefloor assembly 108. For example, when the first payload assembly 110 isattached to the aisle floor assembly 108, the second arms of thesupplemental brackets can be attached to an underside of the aisle floorassembly.

As also shown in FIG. 5, the first payload assembly 110 or, moreparticularly, the first overhead stowbin module 116, includes a firstcenter support wall 138. The first center support wall 138 can beattached to the first stowbin side wall 136 at a position between thefirst pair of end walls 132, 134 such that the first stowage area isdivided into two stowage areas that are each configured to receivestowbins. The first center support wall 138, when attached, can besubstantially perpendicular to the first stowbin side wall 136 andsubstantially parallel to the first pair of end walls 132, 134. Withinexamples, the first center support wall 138 can be positioned to besubstantially equidistant from each of the first pair of end walls 132,134, or could be positioned at a different location.

In line with the discussion above, the first pair of end walls 132, 134,and additionally the first center support wall 138, can increase thestructural integrity of the first payload assembly 110. For example,these components provide vertical support means that also structurallyreinforce the aisle, particularly at the corners where the first stowbinside wall 136 is coupled to the first floor panel 122 and the aislefloor assembly 108. Overall, this can help increase the load-carryingcapability of the overhead payload module 104. Further, the firstplurality of supplemental brackets provide additional structural supportfor the aisle as well.

In alternative implementations, the first payload assembly 110 couldinclude more or less components, or could be assembled in a differentmanner. For instance, an example alternative implementation might notinclude the first center support wall 138, or might include additionalsupport walls between the first pair of end walls 132, 134.

FIG. 6 is an exploded view of the second payload assembly 112 of theoverhead payload module 104, according to an example implementation. Asshown, the second payload assembly 112 comprises a second floor panel140, a second back wall 142, a second ceiling 144, a second pair of sidewalls 146, 148 that together form the second payload module 118 portionof the second payload assembly 112. Further, the second payload assembly112 comprises a second pair of end walls 150, 152 and a second stowbinside wall 154 that together form the second overhead stowbin module 120.In addition, the second pair of end walls 150, 152, the second stowbinside wall 154, and the second floor panel 140 together define a secondstowage area underneath the second floor panel 140 configured to receivestowbins and accessible via the main cabin area 121 of the aircraft 100.In addition to or alternative to the components shown in FIG. 6, thesecond payload assembly 112 can include other walls or other structures,depending on the type of payload area defined. For instance, the secondpayload module 118 may include other walls that enclose a crew restspace.

As shown, one side wall 146 of the second pair of side walls 146, 148 isintegrally formed with one end wall 132 of the second pair of end walls150, 152. And the other side wall 148 of the second pair of side walls146, 148 is integrally formed with the other end wall 134 of the secondpair of end walls 150, 152. Having this type of integral formation canprovide increased structural integrity to the second payload assembly112, such as by reinforcing the second stowbin side wall 154, andpossibly in turn the aisle floor assembly 108. However, in alternativeimplementations, the side walls of the second pair of side walls 146,148 may be independent from the end walls of the second pair of endwalls 150, 152, and thus independently attached when assembling thesecond payload assembly 112.

Further, as shown in FIG. 6, a second plurality of supplementalbrackets, including representative supplemental bracket 155, areattached to the second stowbin side wall 154. Each supplemental bracketof the second plurality of supplemental brackets has a second armattached to the second stowbin side wall 154 and a second arm that canbe attached to the aisle floor assembly 108. For example, when thesecond payload assembly 112 is attached to the aisle floor assembly 108,the second arms of the supplemental brackets can be attached to anunderside of the aisle floor assembly.

As also shown in FIG. 6, the second payload assembly 112 or, moreparticularly, the second overhead stowbin module 120, includes a secondcenter support wall 156. The second center support wall 156 can beattached to the second stowbin side wall 154 at a position between thesecond pair of end walls 150, 152 such that the second stowage area isdivided into two stowage areas that are each configured to receivestowbins. The second center support wall 156, when attached, can besubstantially perpendicular to the second stowbin side wall 154 andsubstantially parallel to the second pair of end walls 150, 152. Withinexamples, the second center support wall 156 can be positioned to besubstantially equidistant from each of the second pair of end walls 150,152, or could be positioned at a different location.

In line with the discussion above, the second pair of end walls 150,152, and additionally the second center support wall 156, can increasethe structural integrity of the second payload assembly 112. Forexample, these components provide vertical support means that alsostructurally reinforce the aisle, particularly at the corners where thesecond stowbin side wall 154 is coupled to the second floor panel 140and the aisle floor assembly 108. Overall, this can help increase theload-carrying capability of the overhead payload module 104. Further,the second plurality of supplemental brackets can provide additionalstructural support for the aisle as well.

In alternative implementations, the second payload assembly 112 couldinclude more or less components, or could be assembled in a differentmanner. For instance, some implementations might not include the secondcenter support wall 156, or might include additional support wallsbetween the second pair of end walls 150, 152.

FIG. 7 is a perspective view of a PSU support assembly 158 attachable toan aisle floor assembly 108 of the overhead payload module 104,according to an example implementation. As shown, the PSU supportassembly 158 can be attached on an underside of the aisle floor assembly108. The PSU support assembly 158 includes two side structures 160, 162and an intermediate structure 164 connecting the two side structures160, 162. Together, the two side structures 160, 162 define atrough-shaped space configured to receive a PSU. The PSU can be a unitof the aircraft 100 above an aisle in the main cabin area 121 thatincludes various components such as reading lights, loudspeakers,illuminated signs, and/or environmental control system components suchas air conditioning vents that regular air and/or pressure.

FIG. 8 is a front view of a PSU support assembly 158 housing a PSU 165,according to an example implementation. The PSU support assembly 158 isattached to the aisle floor assembly 108. To facilitate integration ofthe PSU 165 into the PSU support assembly 158, a distal end of one ofthe two side structures 160, 162, such as distal end 166, can beconfigured to couple to a hinge of the PSU 165 and enable the PSU 165 torotate about the hinge. Further, a distal end of the other of the twoside structures 160, 162, such as distal end 168, can be configured toreceive latches of the PSU 165 for securing the PSU 165 to the PSUsupport assembly 158.

In addition to the end walls and center support walls described above,the overhead payload module 104 can include additional components, suchas a plurality of aisle support structures, that improve the strengthand reinforcement of the aisle. Due to high loads that could be placedon the overhead payload module 104 or similar structure in practice.Further, the end walls, center support walls, and other componentsdescribed herein can increase the stiffness of the aisle as well, suchthat the resonant frequency of the aisle structure has a reducedresonant frequency that is different from the resonant frequency of theaircraft 100.

FIG. 9 is a perspective view of a plurality of aisle support structuresattached along a length of the aisle floor assembly 108, according to anexample implementation. In particular, the plurality of aisle supportstructures includes a first aisle support structure 170, a second aislesupport structure 172, and a center aisle support structure 174. Asshown, each of the plurality of aisle support structures 170, 172, 174includes (i) a first support bracket, such as representative firstsupport bracket 176, (ii) a second support bracket positioned oppositethe first support bracket, such as representative second support bracket178, and (iii) a cross member attached between the aisle floor assembly108 and the first and second support brackets, such as representativecross member 180.

As shown the center aisle support structure 174 is positionedsubstantially equidistant from the first aisle support structure 170 andthe second aisle support structure 172. In alternative implementations,however, the center aisle support structure 174 could be positionedelsewhere.

FIG. 10 is a perspective view of the plurality of aisle supportstructures 170, 172, 174 attached to the aisle floor assembly 108 and toother components of the overhead payload module 104, according to anexample implementation. As shown, one support bracket of the first aislesupport structure 170 is attached to end wall 132 of the first pair ofend walls 132, 134, and the other support bracket of the first aislesupport structure 170 is attached to end wall 150 of the second pair ofend walls 150, 152. Further, one support bracket of the second aislesupport structure 172 is attached to end wall 134 of the first pair ofend walls 132, 134, and the other support bracket of the second aislesupport structure 172 is attached to end wall 152 of the second pair ofend walls 150, 152. Still further, one support bracket of the centeraisle support structure 174 is attached to the first center support wall138 and the other support bracket of the center aisle support structure174 is attached to the second center support wall 156.

In some implementations, one or more support brackets on the side of theoverhead payload module 104 where the first payload assembly is locatedcan also be attached to a first stowbin side wall 136. Likewise, one ormore support brackets on the side of the overhead payload module 104where the second payload assembly is located can also be attached to asecond stowbin side wall 154. Doing so might provide even more supportfor the aisle and even further increase the structural integrity and/orthe load-carrying capability of the overhead payload module 104.Alternatively, some or all of the support brackets may contact thestowbin side walls without being attached.

FIG. 11 is a perspective view of representative first support bracket176 of the first aisle support structure 170, according to an exampleimplementation. However, the support bracket shown in FIG. 11 is a formthat any of the respective first support brackets of the plurality ofaisle support structures 170, 172, 174 could take. As shown, the firstsupport bracket 176 includes a first arm 182 that, if located on theside of the overhead payload module 104 where the first payload assemblyis located, can be attached to the first payload assembly 110 (e.g., toend wall 132, end wall 134, or the first center support wall 138), or,if located on the side of the overhead payload module 104 where thesecond payload assembly is located, can be attached to the secondpayload assembly 112 (e.g., to end wall 150, end wall 152, or the secondcenter support wall 156). The first support bracket 176 also includes asecond arm 184 that can be attached to the aisle floor assembly 108.

In addition, the first support bracket 176 includes a first stowbinpivot fitting 186 integrally formed with the first arm 182 and thesecond arm 184. The first stowbin pivot fitting 186 defines an axisabout which a stowbin can rotate when the stowbin is rotatably attachedto the first stowbin pivot fitting 186.

FIG. 12 is another perspective view of the first aisle support structure170, according to an example implementation. In addition to showing thefirst arm 182, the second arm 184, and the first stowbin pivot fitting186 of the first support bracket 176, FIG. 12 shows a first arm 188, asecond arm 190, and a second stowbin pivot fitting 192 of the secondsupport bracket 178. It should be noted that the second support bracket178 in FIG. 12 is a form that any of the respective second supportbrackets of the plurality of aisle support structures 170, 172, 174could take. The second stowbin pivot fitting 192 is integrally formedwith the first arm 188 and the second arm 190 and defines an axis aboutwhich a stowbin can rotate when the stowbin is rotatably attached to thesecond stowbin pivot fitting 192.

Further, the first arm 182 of the first support bracket 176 is shown tobe attached on one side to end wall 132. An opposite side of the firstarm 182 has engagement surface with the first stowbin side wall 136.Still further, the first arm 188 of the second support bracket 178 isshown to be attached on one side to end wall 150. An opposite side ofthe first arm 188 has an engagement surface with the second stowbin sidewall 154. In alternative implementations, however, the first arm 182 ofthe first support bracket 176 could be attached to the first stowbinside wall 136, and the first arm 188 of the second support bracket 178could be attached to the second stowbin side wall 154.

Also shown in FIG. 12 is the cross member 180 of the first aisle supportstructure 170. In particular, the cross member 180 has a first endportion 194 attached between the aisle floor assembly 108 and the firstsupport bracket 176 (namely, between the aisle floor assembly 108 andthe second arm 184 of the first support bracket 176). Further, the crossmember 180 has a second end portion 196 attached between the aisle floorassembly 108 and the second support bracket 178 (namely, between theaisle floor assembly 108 and the second arm 190 of the second supportbracket 178). In some implementations, the length of the first arms 182,188 and the second arms 184, 190 may vary. For instance, the second arms184, 190 may extend further towards each other, thereby contacting alarger surface of the cross member 180.

The cross member 180, along with any other cross members of any otheraisle support structures along the length of the aisle floor assembly108, can provide support underneath the aisle floor assembly 108, andstrengthen and stiffen the aisle. Furthermore, each aisle supportstructure can serve as a load path from one side of the overhead payloadmodule 104 to the other, to help the overhead payload module 104 carryloads.

In some implementations, one or more first arms of the support bracketson the side of the overhead payload module 104 where the first payloadassembly is located could include a surface (e.g., a flat, rectangularsurface) on which the first floor panel 122 can rest or to which thefirst floor panel 122 could be attached. Likewise, one or more secondarms of the support brackets on the side of the overhead payload module104 where the second payload assembly is located could include such asurface on which the second floor panel 140 can rest or to which thesecond floor panel 140 could be attached.

The above-described arrangement and attachments of support structures,namely, the aisle support structures shown in FIGS. 9-12, can providevarious advantages, such as improving the strength and reinforcement ofthe aisle as discussed above. Further, the support brackets of thesestructures can resist rotation, and a rotational moment of inertia atthe corners of the aisle (e.g., where the second stowbin side wall 154is coupled to the second floor panel 140 and the aisle floor assembly108) can be increased.

FIG. 13 is a perspective view of the overhead payload module 104including a first plurality of blade fittings 200, 202, 204, accordingto an example implementation. In particular, the first plurality ofblade fittings 200, 202, 204 are attached along a length of an exteriorof the overhead payload module 104 on the side of the overhead payloadmodule 104 where the first payload assembly is located. The firstplurality of blade fittings 200, 202, 204 includes a first pair of bladefittings 200, 202 and a first center blade fitting 204. In alternativeimplementations, more or less blade fittings could be attached to theoverhead payload module 104 on the side of the overhead payload module104 where the first payload assembly is located. The first pair of bladefittings 200, 202 are on opposite sides of, and spatially separatedfrom, the first center blade fitting 204.

As shown, each of the first plurality of blade fittings 200, 202, 204have a bracket portion (e.g., bracket portion 222 shown in FIG. 16 orbracket portion 222 shown in FIG. 19) attached to the first payloadmodule 114. A first bracket arm (e.g., first bracket arm 226 shown inFIG. 16 or first bracket arm 254 shown in FIG. 19) of the bracketportion extends towards a center longitudinal plane of the overheadpayload module 104 and is attached to an underside of the first floorpanel 122. A second bracket arm (e.g., second bracket arm 228 shown inFIG. 16 or second bracket arm 256 shown in FIG. 19) of the bracketportion is substantially perpendicular to the first bracket arm andattached to an exterior surface of the first back wall 124.

In order to locally strengthen the attachment between each of the firstplurality of blade fittings 200, 202, 204 and the overhead payloadmodule 104, one or more optional metal sheets 206, such as aluminumsheets, could be attached between each of the first plurality of bladefittings 200, 202, 204 and the overhead payload module 104 on anexterior of the overhead payload module 104 at the locations where eachsuch blade fitting is attached to the overhead payload module 104. Thefirst plurality of blade fittings 200, 202, 204 could be attached to theoverhead payload module 104 after the metal sheets are attached on theexterior of the overhead payload module 104 to one or both of the firstfloor panel 122 and the first back wall 124. Additionally oralternatively, one or more metal sheets could be attached on an interiorof the overhead payload module 104 onto surfaces opposite the surfacesthat will engage with the first plurality of blade fittings 200, 202,204.

FIG. 14 is another perspective view of the overhead payload module 104including a second plurality of blade fittings 208, 210, 212, accordingto an example implementation. In particular, the second plurality ofblade fittings 208, 210, 212 are attached along a length of an exteriorof the overhead payload module 104 on the side of the overhead payloadmodule 104 where the second payload assembly is located. The secondplurality of blade fittings 208, 210, 212 includes a second pair ofblade fittings 208, 210 and a second center blade fitting 212. Inalternative implementations, more or less blade fittings could beattached to the overhead payload module 104 on the side of the overheadpayload module 104 where the second payload assembly is located. Thesecond pair of blade fittings 208, 210 are on opposite sides of, andspatially separated from, the second center blade fitting 212.

As shown, each of the second plurality of blade fittings 208, 210, 212have a bracket portion (e.g., bracket portion 222 shown in FIG. 16 orbracket portion 222 shown in FIG. 19) attached to the second payloadmodule 118. A first bracket arm (e.g., first bracket arm 226 shown inFIG. 16 or first bracket arm 254 shown in FIG. 19) of the bracketportion extends towards a center longitudinal plane of the overheadpayload module 104 and is attached to an underside of the second floorpanel 140. A second bracket arm (e.g., second bracket arm 228 shown inFIG. 16 or second bracket arm 256 shown in FIG. 19) of the bracketportion is substantially perpendicular to the first bracket arm andattached to an exterior surface of the second back wall 142.

In order to locally strengthen the attachment between each of the secondplurality of blade fittings 208, 210, 212 and the overhead payloadmodule 104, one or more optional metal sheets 206 could be attachedbetween each of the second plurality of blade fittings 208, 210, 212 andthe overhead payload module 104 on an exterior (and/or interior) of theoverhead payload module 104 at the locations where each such bladefitting is attached to the overhead payload module 104, such asdescribed above with respect to the first plurality of blade fittings200, 202, 204.

Although not explicitly shown in FIG. 13 and FIG. 14, the firstplurality of blade fittings 200, 202, 204 and the second plurality ofblade fittings 208, 210, 212 may be substantially aligned with oneanother. For instance, blade fitting 200 may be directly opposite bladefitting 208 such that they are aligned (e.g., such that their respectivefirst arms fall along the same axis running through the overhead payloadmodule 104). Blade fitting 202 and blade fitting 210 may be similarlyarranged with respect to one another, and blade fitting 204 and bladefitting 212 may be similarly arranged as well with respect to oneanother. In alternative implementations, the first plurality of bladefittings 200, 202, 204 and the second plurality of blade fittings 208,210, 212 might not be substantially aligned with one another.

Each of the above-described blade fittings can be configured forattaching to a support rail assembly of the aircraft 100 so as to attachthe overhead payload module 104 to the support rail assembly within theaircraft 100.

As also shown in FIG. 14, multiple stowbins 117 are installed in theoverhead payload module 104.

FIG. 15 is a perspective view of the overhead payload module 104attached to a support rail assembly 214, according to an exampleimplementation. The support rail assembly includes a first support rail216 and a second support rail 218. The first plurality of blade fittings200, 202, 204 are attached to the first support rail 216. Although notshown in FIG. 15, the second plurality of blade fittings 208, 210, 212are attached to the second support rail 218.

FIG. 16 is a side view of a blade fitting 220, according to an exampleimplementation. The blade fitting 220 shown in FIG. 16 is arepresentative example of a form that one or more of the blade fittingsdescribed herein could take.

The blade fitting 220 includes a bracket portion 222 and a hook portion224. The bracket portion 222 is configured as described above, with afirst bracket arm 226 attachable to one of the floor panels and that,when attached, would extend towards a center longitudinal plane of theoverhead payload module 104. The bracket portion also includes a secondbracket arm 228 attachable to one of the back walls. The first bracketarm 226 and the second bracket arm 228 are shown to be substantiallyperpendicular with one another. Further, when attached, the secondbracket arm 228 may be substantially parallel to a lateral axis of theoverhead payload module 104.

The hook portion 224 protrudes from the second bracket arm 228. A distalend 230 of the hook portion 224 includes a bearing 232. As shown, thedistal end 230 is substantially parallel to the second bracket arm 228.When the blade fitting 220 is attached to one of the support rails, atleast a portion of the distal end 230 of the hook portion 224 can beinserted into an opening in the support rail. A fastener can then beinserted through a bore in one side of the support rail, through thebearing 232, and through a bore in another side of the support rail,before being secured in place. Within examples, a bolt and washer couldbe used to fasten the blade fitting 220 to the support rail. Otherexamples of fasteners are possible as well. In alternativeimplementations, other bracket portion and/or hook portion geometriesare possible.

The design of the blade fitting 220 described above can improve themanner in which the overhead payload module 104 is installed in theaircraft 100. For instance, as will be described in greater detailbelow, the hook portion 224 of the blade fitting 220 can be lifteddirectly into an underside of a respective rail of the support railassembly 214 and then secured.

FIG. 17 is a perspective view of the blade fitting 220 and a supportrail 234, and another side view of the blade fitting 220, according toan example implementation. In particular, the perspective view of theblade fitting 220 depicts how the hook portion 224 of the blade fitting220 would be secured to the support rail 234. And the side view of theblade fitting 220 depicts the blade fitting 220 when it is secured tothe support rail 234. The support rail 234 shown in FIG. 17 could be aportion of either the first support rail 216 or the second support rail218.

In addition, as shown, the first bracket arm 226 includes two protrudingears 236, 238 and the second bracket arm 228 includes four protrudingears 240, 242, 244, 246. Each such ear includes a bore configured forreceiving a fastener. When attached to the overhead payload module 104,the fastener can be inserted through the bore. Other means for attachingthe blade fitting 220 to the overhead payload module 104 are possible aswell.

Further, as shown in the side view, the distal end of the blade fitting220 has been inserted through an opening 248 in an underside of thesupport rail 234 and a fastener 250 has been used to attach the bladefitting 220 to the support rail 234.

FIG. 18 depicts an arrangement of blade fittings of the overhead payloadmodule 104 used to attach the overhead payload module 104 to the supportrail assembly 214, according to an example implementation. Each bladefitting of the overhead payload module 104 could have any type ofbearing, such as spherical bearing or a non-spherical, fixed bearing, byway of example. There may be certain advantages to which blade fittingsdo and do not have certain types of bearings, however. One such exampleis described with respect to FIG. 18, which shows various blade fittingsrelative to each other.

As shown in FIG. 18, the bearing of the first center blade fitting 204is a non-spherical, fixed bearing, but the bearings of the second centerblade fitting 212, the first pair of blade fittings 200, 202, and thesecond pair of blade fittings 208, 210, are all spherical bearings. Assuch, the overhead payload module 104 can be attached more rigidly tothe second support rail 218, on the side of the second plurality ofblade fittings 208, 210, 212, than to the first support rail 216.Phrased another way, one side (i.e., the side with the non-spherical,fixed bearing) has what may be referred to as a fixed bearingarrangement, and the other side (i.e., the side with all sphericalbearings) has what may be referred to as a floating bearing arrangement.The “floating” side can thus have more freedom of movement to helpcompensate for excessive loads and potential misalignment (and alsoperhaps any potential thermal expansion or contraction). In addition,this can allow loads to be directed into the support rail assembly 214in a tailored fashion. This can also help the combination of theoverhead payload module 104 and the support rail assembly 214 todistribute loads. Other advantages are possible as well. Furthermore, inalternative implementations or in conjunction with examples discussedherein, one or more other blade fittings on the fixed bearingarrangement side could have non-spherical bearings as well. Otherarrangements of spherical/non-spherical bearings are possible. Forexample, instead of a non-spherical, fixed bearing, a bushing could beemployed. Additionally or alternatively, the second center blade fitting212 could be the non-spherical, fixed bearing (or bushing).

FIG. 19 is a perspective view of another type of blade fitting,according to an example implementation. Any one or more of the bladefittings described herein could take the form shown in FIG. 19. Forpurposes of example, however, FIG. 19 shows the blade fitting as beingattached to the first payload module 114.

As shown, the blade fitting includes a bracket portion 252 (whichincludes bracket arms 254 and 256) attached to an exterior of one of thefirst or second payload modules. For purposes of example, FIG. 19 labelsthe payload module as the first payload module 114. Similar to bladefitting 220, the bracket portion 252 of the blade fitting in FIG. 19includes (i) a first bracket arm 254 extending towards a centerlongitudinal plane of the overhead payload module 104 and attached tothe first floor panel 122 and (ii) a second bracket arm 256 attached tothe first back wall 124. Further, the blade fitting includes aconnecting portion 258 that extends away from the center longitudinalplane of the overhead payload module 104, in a direction that issubstantially opposite the direction that the first bracket arm 254extends. A distal end of the connecting portion 258 can include aplurality of bores (not shown) that are configured to receive aplurality of fasteners.

In addition, the blade fitting includes a hook portion 260. The hookportion 260 includes a bushing end 262 that is adjustably attached tothe connecting portion 258 via the plurality of fasteners. Inparticular, the bushing end includes a plurality of eccentric bushingsconfigured to receive the plurality of fasteners (e.g., bolts). Each ofthe eccentric bushings can have its hole drilled off-center such that,as the bushing is rotated, the hole changes location in two directions.

The region in which the plurality of fasteners, the plurality of boresof the connecting portion 258, and the plurality of eccentric bushingsare located is denoted as region 264. Although three of each are shown,in alternative implementations there could be more or less bores,fasteners, and bushings used to attach the hook portion 260 to theconnecting portion 258. Lastly, the hook portion 260 includes a distalend 266, which includes a bearing 268. Similar to the other bladefittings described above, the distal end 266 can be configured to beinserted into openings of the support rail assembly 214 and attached viaa fastener.

The hook portion 260, serving as a lug, is not part of the main portion(e.g., the bracket portion 252 and the connecting portion 258) of theblade fitting, and the plurality of eccentric bushings can be rotated tomove the lug around. As so configured, more adjustability built into theblade fitting. More particularly, the eccentric bushings can serve as atolerance backup in scenarios where there could be potentialmisalignment of the bearing 268 with the holes in the support rail towhich the blade fitting of FIG. 19 is being secured. For example, if thebearing 268 does not line up with the holes in the support rail, themovement provided by the eccentric bushings can allow the hook portion260, and thus the bearing 268, to be brought into alignment with theholes.

Various methods will now be described. First, FIG. 20 shows a flowchartof an example method 300 for balancing load in, and reinforcing an aislestructure of, an overhead payload module of an aircraft, according to anexample implementation. FIGS. 21-24 then include functions associatedwith method 300.

Next, FIG. 25 shows a flowchart of an example method 400 for assemblingthe overhead payload module of the aircraft, according to an exampleimplementation. FIGS. 26-28 then include functions associated withmethod 400.

Finally, FIG. 29 shows a flowchart of an example method 500 forinstalling the overhead payload module in the aircraft, according to anexample implementation. FIGS. 30-31 then include functions associatedwith method 500.

Method 300, method 400, and method 500 present examples of methods thatcould be used with the aircraft 100 shown in FIG. 1 or with componentsof the aircraft 100 such as the overhead payload module 104 describedabove. Further, devices or systems, such as devices used formanufacturing aircrafts or components thereof, may be used or configuredto perform functions presented in FIGS. 20, 25, and 29. In otherexamples, components of the devices and/or systems may be arranged to beadapted to, capable of, or suited for performing the functions, such aswhen operated in a specific manner.

Method 300 may include one or more operations, functions, or actions asillustrated by one or more of blocks 302-306. Method 400 may include oneor more operations, functions, or actions as illustrated by one or moreof blocks 402-408. And method 500 may include one or more operations,functions, or actions as illustrated by one or more of blocks 502-504.Although the blocks are illustrated in a sequential order, these blocksmay also be performed in parallel, and/or in a different order thanthose described herein. Also, the various blocks may be combined intofewer blocks, divided into additional blocks, and/or removed based uponthe desired implementation.

Referring now to method 300 of FIG. 20, at block 302, the method 300includes attaching a first payload assembly to (i) a ceiling assemblyand (ii) an aisle floor assembly to form a first side of the overheadpayload module. The first payload assembly can include a first payloadmodule comprising a first floor panel. The first payload assembly canalso include a first overhead stowbin module structurally integratedwith the first payload module and having a first stowage area configuredto receive stowbins and accessible via a main cabin area of theaircraft. The first overhead stowbin module can include a first pair ofend walls attached to a first stowbin side wall. Further, the first pairof end walls, the first stowbin side wall, and the first floor panel candefine the first stowage area.

At block 304, the method 300 includes attaching a second payloadassembly to (i) the ceiling assembly and (ii) the aisle floor assemblyto form a second side of the overhead payload module. The second payloadassembly can be positioned opposite the first payload assembly to forman aisle therebetween. The second payload assembly can include a secondpayload module comprising a second floor panel. The second payloadassembly can also include a second overhead stowbin module structurallyintegrated with the second payload module and having a second stowagearea configured to receive stowbins and accessible via the main cabinarea of the aircraft. The second overhead stowbin module can include asecond pair of end walls attached to a second stowbin side wall. Thesecond pair of end walls, the second stowbin side wall, and the secondfloor panel can define the second stowage area.

At block 306, the method 300 includes attaching a plurality of aislesupport structures to the overhead payload module at a plurality ofdifferent locations along a length of the aisle floor assembly.Attaching the plurality of aisle support structures to the overheadpayload module can involve, for each aisle support structure of theplurality of aisle support structures: attaching a first arm of a firstsupport bracket to the first payload assembly and a second arm of thefirst support bracket to the aisle floor assembly, attaching a first armof a second support bracket, positioned opposite the first supportbracket, to the second payload assembly and a second arm of the secondsupport bracket to the aisle floor assembly, and attaching a first endportion of a cross member between the aisle floor assembly and the firstsupport bracket and a second end portion of the cross member between theaisle floor assembly and the second support bracket.

FIG. 21 shows a flowchart of an example method for use with the method300, according to an example implementation. At block 308, functionsinclude attaching a first center support wall to the first stowbin sidewall. The first center support wall can be attached to the first stowbinside wall between the first pair of end walls to divide the firststowage area into two stowage areas each configured to receive stowbins,such that the first center support wall is substantially perpendicularto the first stowbin side wall and substantially parallel to the firstpair of end walls. At block 310, functions include attaching a secondcenter support wall to the second stowbin side wall. The second centersupport wall can be attached to the second stowbin side wall between thesecond pair of end walls to divide the second stowage area into twostowage areas each configured to receive stowbins, such that the secondcenter support wall is substantially perpendicular to the second stowbinside wall and substantially parallel to the second pair of end walls.

FIG. 22 shows a flowchart of an example method for performing theattaching as shown in block 306, particularly in view of the attachingshown in blocks 308 and 310, according to an example implementation. Atblock 312, functions include attaching a first aisle support structureto a first end wall of the first pair of end walls and a first end wallof the second pair of end walls. At block 314, functions includeattaching a second aisle support structure to a second end wall of thefirst pair of end walls and a second end wall of the second pair of endwalls. At block 316, functions include attaching a center aisle supportstructure to the first center support wall and the second center supportwall.

FIG. 23 shows a flowchart of another example method for use with themethod 300, according to an example implementation. At block 318,functions relate to a method for attaching each supplemental bracket ofa first plurality of supplemental brackets. In particular, at block 318,functions include attaching a first arm of the supplemental bracket tothe first stowbin side wall and a second arm of the supplemental bracketto the aisle floor assembly. At block 320, functions relate to a methodfor attaching each supplemental bracket of a second plurality ofsupplemental brackets. In particular, at block 320, functions includeattaching a first arm of the supplemental bracket to the second stowbinside wall and a second arm of the supplemental bracket to the aislefloor assembly.

FIG. 24 shows a flowchart of another example method for use with themethod 300, according to an example implementation. At block 322,functions include attaching a passenger service unit (PSU) supportassembly to the aisle floor assembly. The PSU support assembly caninclude two side structures and an intermediate structure connecting thetwo side structures. The two side structures and the intermediatestructure can define a trough-shaped space configured to receive a PSU.A distal end of one side structure of the two side structures can beconfigured to couple to a hinge of the PSU and enable the PSU to rotateabout the hinge. A distal end of another side structure of the two sidestructures can be configured to receive latches of the PSU for securingthe PSU to the PSU support assembly.

Referring now to method 400 of FIG. 25, at block 402, the method 400includes attaching a first payload assembly to (i) a ceiling assemblyand (ii) an aisle floor assembly to form a first side of the overheadpayload module. The first payload assembly can include a first payloadmodule comprising a first floor panel and a first back wall. The firstpayload assembly can also include a first overhead stowbin modulestructurally integrated with the first payload module and having a firststowage area configured to receive stowbins and accessible via a maincabin area of the aircraft.

At block 404, the method 400 includes attaching a second payloadassembly to (i) the ceiling assembly and (ii) the aisle floor assemblyto form a second side of the overhead payload module. The second payloadassembly can be positioned opposite the first payload assembly to forman aisle therebetween. The second payload assembly can include a secondpayload module comprising a second floor panel and a second back wall.The second payload assembly can also include a second overhead stowbinmodule structurally integrated with the second payload module and havinga second stowage area configured to receive stowbins and accessible viathe main cabin area of the aircraft.

At block 406, the method 400 includes attaching a first plurality ofblade fittings along a length of an exterior of the first payload moduleto the first back wall and the first floor panel.

At block 408, the method 400 includes attaching a second plurality ofblade fittings along a length of an exterior of the second payloadmodule to the second back wall and the second floor panel. Each bladefitting of the first plurality of blade fittings and the secondplurality of blade fittings is configured for attaching to a supportrail assembly of the aircraft so as to attach the overhead payloadmodule to the support rail assembly within the aircraft.

FIG. 26 shows a flowchart of an example method for performing theattaching as shown in block 406, according to an example implementation.At block 410, functions relate to a method for attaching each bladefitting of the first plurality of blade fittings. In particular, atblock 410, functions include attaching (i) a first bracket arm of theblade fitting to the first floor panel and (ii) a second bracket arm ofthe blade fitting to the first back wall.

In addition, FIG. 26 shows a flowchart of another example method forperforming the attaching as shown in block 408, according to an exampleimplementation. At block 412, functions relate to a method for attachingeach blade fitting of the second plurality of blade fittings. Inparticular, at block 412, functions include attaching (i) a firstbracket arm of the blade fitting to the second floor panel and (ii) asecond bracket arm of the blade fitting to the second back wall. A hookportion can protrude from the second bracket arm of each blade fittingof the first plurality of blade fittings and the second plurality ofblade fittings, and a distal end of the hook portion can include abearing and can be configured to be inserted into an opening of thesupport rail assembly and attached to the support rail assembly with afastener inserted through the support rail assembly and the bearing.

FIG. 27 shows a flowchart of another example method for performing theattaching as shown in block 406, according to an example implementation.At block 414, functions include attaching a first center blade fittingand a first pair of blade fittings spatially separated from the firstcenter blade fitting on opposite sides of the first center bladefitting.

In addition, FIG. 27 shows a flowchart of another example method forperforming the attaching as shown in block 412, according to an exampleimplementation. At block 416, functions include attaching a secondcenter blade fitting and a second pair of blade fittings spatiallyseparated from the second center blade fitting on opposite sides of thesecond center blade fitting. The bearing of the first center bladefitting can be a non-spherical, fixed bearing, and the bearing of thesecond center blade fitting, the first pair of blade fittings, and thesecond pair of blade fittings can be a spherical bearing.

In some implementations, some functions may be performed before thefunctions at blocks 406 and 408 are performed. FIG. 28 shows a flowchartof an example method for use with the method of FIG. 25, according to anexample implementation. In particular, before attaching the firstplurality of blade fittings along the length of the exterior of thefirst payload module to the first back wall and the first floor paneland attaching the second plurality of blade fittings along the length ofthe exterior of the second payload module to the second back wall andthe second floor panel, functions include attaching one or more metalsheets to each location of a plurality of locations on the first backwall, the first floor panel, the second back wall, and the second floorpanel, as shown in block 418.

In addition, FIG. 28 shows a flowchart of another example method forperforming the attaching as shown in block 406, according to an exampleimplementation. At block 420, functions include attaching the firstplurality of blade fittings to the one or more metal sheets.

Further, FIG. 28 shows a flowchart of another example method forperforming the attaching as shown in block 408, according to an exampleimplementation. At block 422, functions include attaching the secondplurality of blade fittings to the one or more metal sheets.

Referring now to method 500 of FIG. 29, at block 502, the method 500includes providing a support rail assembly in the aircraft. The supportrail assembly can include a first support rail positioned on a firstside of the aircraft and a second support rail positioned on a secondside of the aircraft opposite the first side. The first support rail andthe second support rail can be substantially parallel and substantiallyplanar.

At block 504, the method 500 includes attaching the overhead payloadmodule to the support rail assembly. The overhead payload module can beattached to the support rail assembly to position the overhead payloadmodule above a main cabin area of the aircraft and between the firstsupport rail and the second support rail. The overhead payload modulecan include a first payload assembly and a second payload assembly. Thefirst payload assembly can include a first payload module, a firstoverhead stowbin module structurally integrated with the first payloadmodule and having a first stowage area, and a first plurality of bladefittings attached along a length of an exterior of the first payloadmodule. Each blade fitting of the first plurality of blade fittings caninclude bracket portion attached to a first back wall and a first floorpanel of the first payload module and a hook portion protruding from thebracket portion and attachable to the first support rail. The secondpayload assembly can include a second payload module, a second overheadstowbin module structurally integrated with the second payload moduleand having a second stowage area, and a second plurality of bladefittings attached along a length of an exterior of the second payloadmodule. Each blade fitting of the second plurality of blade fittings caninclude bracket portion attached to a second back wall and a secondfloor panel of the second payload module and a hook portion protrudingfrom the bracket portion and attachable to the second support rail.Attaching the overhead payload module to the support rail assembly toposition the overhead payload module above the main cabin area of theaircraft and between the first support rail and the second support railcan involve attaching the hook portion of each blade fitting of thefirst plurality of blade fittings to the first support rail andattaching the hook portion of each blade fitting of the second pluralityof blade fittings to the second support rail.

FIG. 30 shows a flowchart of an example method for performing theattaching as shown in block 504, according to an example implementation.In particular, FIG. 29 shows a flowchart of an example method forattaching the hook portion of each blade fitting of the first pluralityof blade fittings to the first support rail, as well as an examplemethod for attaching the hook portion of each blade fitting of thesecond plurality of blade fittings to the second support rail. In eithercase, for each blade fitting of the first and second plurality of bladefittings, a respective hook portion is inserted into a respectiveopening in a respective support rail. For each blade fitting of thefirst plurality of blade fittings, for instance, a respective hookportion is inserted into a respective opening of a first plurality ofopenings in the first support rail. And for each blade fitting of thesecond plurality of blade fittings, a respective hook portion isinserted into a respective opening of a second plurality of openings inthe second support rail.

For the first plurality of blade fittings, for instance, at block 506,functions include inserting the hook portion into a respective openingof a first plurality of openings in the first support rail and attachingthe hook portion to the first support rail via a fastener. The fastenercan be inserted through the first support rail and a bearing at a distalend of the hook portion. For the second plurality of blade fittings, atblock 508, functions include inserting the hook portion into arespective opening of a second plurality of openings in the secondsupport rail and attaching the hook portion to the second support railvia a fastener. The fastener can be inserted through the second supportrail and a bearing at a distal end of the hook portion.

FIG. 31 shows a flowchart of an example method for performing theattaching as shown in block 506, according to an example implementation.In particular, FIG. 31 shows a flowchart of an example method forattaching the hook portion of each blade fitting of the first pluralityof blade fittings to the first support rail. At block 510, functionsinclude (i) attaching a hook portion of a first center blade fitting ofthe first plurality of blade fittings to the first support rail via afastener inserted through the first support rail and a non-spherical,fixed bearing and (ii) attaching hook portions of a first pair of bladefittings of the first plurality of blade fittings to the first supportrail via fasteners inserted through the first support rail and sphericalbearings. The non-spherical, fixed bearing can be at a distal end of thehook portion of the first center blade fitting. The spherical bearingscan be at distal ends of the hook portions of the first pair of bladefittings. The first pair of blade fittings can be spatially separatedfrom the first center blade fitting on opposite sides of the firstcenter blade fitting.

FIG. 31 also shows a flowchart of an example method for performing theattaching as shown in block 508, according to an example implementation.In particular, FIG. 31 shows a flowchart of an example method forattaching the hook portion of each blade fitting of the second pluralityof blade fittings to the second support rail. At block 512, functionsinclude attaching the hook portion of each blade fitting of the secondplurality of blade fittings to the second support rail via a fastenerinserted through the second support rail and a spherical bearing. Thespherical bearing can be at the distal end of the hook portion.

By the term “substantially” and “about” used herein, it is meant thatthe recited characteristic, parameter, or value need not be achievedexactly, but that deviations or variations, including for example,tolerances, measurement error, measurement accuracy limitations andother factors known to skill in the art, may occur in amounts that donot preclude the effect the characteristic was intended to provide.

Different examples of the system(s), device(s), and method(s) disclosedherein include a variety of components, features, and functionalities.It should be understood that the various examples of the system(s),device(s), and method(s) disclosed herein may include any of thecomponents, features, and functionalities of any of the other examplesof the system(s), device(s), and method(s) disclosed herein in anycombination or any sub-combination, and all of such possibilities areintended to be within the scope of the disclosure.

The description of the different advantageous arrangements has beenpresented for purposes of illustration and description, and is notintended to be exhaustive or limited to the examples in the formdisclosed. Many modifications and variations will be apparent to thoseof ordinary skill in the art. Further, different advantageous examplesmay describe different advantages as compared to other advantageousexamples. The example or examples selected are chosen and described inorder to best explain the principles of the examples, the practicalapplication, and to enable others of ordinary skill in the art tounderstand the disclosure for various examples with variousmodifications as are suited to the particular use contemplated.

What is claimed is:
 1. An overhead payload module for installation in anaircraft, the overhead payload module comprising: an aisle floorassembly; a first payload assembly attached to the aisle floor assemblyto form a first side of the overhead payload module, wherein the firstpayload assembly comprises: a first payload module, and a first overheadstowbin module structurally integrated with the first payload module andhaving a first stowage area configured to receive stowbins, and a secondpayload assembly attached to the aisle floor assembly to form a secondside of the overhead payload module, wherein the second payload assemblyis positioned opposite the first payload assembly to form an aisletherebetween, wherein the second payload assembly comprises: a secondpayload module, and a second overhead stowbin module structurallyintegrated with the second payload module and having a second stowagearea configured to receive stowbins; and at least one aisle supportstructure attached to the overhead payload module at one or morelocations along a length of the aisle floor assembly, wherein each aislesupport structure of the at least one aisle support structure comprises:a first support bracket having a first arm attached to the first payloadassembly and a second arm attached to the aisle floor assembly, a secondsupport bracket positioned opposite the first support bracket and havinga first arm attached to the second payload assembly and a second armattached to the aisle floor assembly, and a cross member having a firstend portion attached to the aisle floor assembly and the first supportbracket and having a second end portion attached to the aisle floorassembly and the second support bracket.
 2. The overhead payload moduleof claim 1, wherein the first overhead stowbin module comprises a firststowbin side wall, a first pair of end walls, and a first center supportwall that is attached to first stowbin side wall between the first pairof end walls and that divides the first stowage area into two stowageareas each configured to receive stowbins, and wherein the secondoverhead stowbin module comprises a second stowbin side wall, a secondpair of end walls, and a second center support wall that is attached tothe second stowbin side wall between the second pair of end walls andthat divides the second stowage area into two stowage areas eachconfigured to receive stowbins.
 3. The overhead payload module of claim2, wherein the at least one aisle support structure comprises two ormore of: a first aisle support structure attached to a first end wall ofthe first pair of end walls and a first end wall of the second pair ofend walls, a second aisle support structure attached to a second endwall of the first pair of end walls and a second end wall of the secondpair of end walls, or a center aisle support structure attached to thefirst center support wall and the second center support wall.
 4. Theoverhead payload module of claim 3, wherein the at least one aislesupport structure comprises the first aisle support structure, thesecond aisle support structure, and the center aisle support structure,and wherein the center aisle support structure is positionedsubstantially equidistant from the first aisle support structure and thesecond aisle support structure.
 5. The overhead payload module of claim1, wherein the first payload assembly further comprises a firstplurality of supplemental brackets attached to the first overheadstowbin module and to the aisle floor assembly, and wherein the secondpayload assembly further comprises a second plurality of supplementalbrackets attached to the second overhead stowbin module and to the aislefloor assembly.
 6. The overhead payload module of claim 1, wherein thefirst payload module comprises a first pair of side walls and a firstpair of end walls, wherein the second payload module further comprises asecond pair of side walls and a second pair of end walls, wherein thefirst pair of end walls are integrally formed with the first pair ofside walls of the first payload module, and wherein the second pair ofend walls are integrally formed with the second pair of side walls ofthe second payload module.
 7. The overhead payload module of claim 1,wherein the first support bracket includes a first stowbin pivot fittingintegrally formed with the first arm and the second arm of the firstsupport bracket, wherein the second support bracket includes a secondstowbin pivot fitting integrally formed with the first arm and thesecond arm of the second support bracket, and wherein each stowbin pivotfitting of the first stowbin pivot fitting and the second stowbin pivotfitting defines an axis about which a stowbin rotates when the stowbinis rotatably attached to the stowbin pivot fitting.
 8. An aircraftcomprising: a fuselage; an overhead payload module comprising: an aislefloor assembly positioned above a main cabin area of the aircraft, afirst payload assembly attached the aisle floor assembly to form a firstside of the overhead payload module, wherein the first payload assemblycomprises: a first payload module, and a first overhead stowbin modulestructurally integrated with the first payload module and having a firststowage area configured to receive stowbins, and a second payloadassembly attached to the aisle floor assembly to form a second side ofthe overhead payload module, wherein the second payload assembly ispositioned opposite the first payload assembly to form an aisletherebetween, wherein the second payload assembly comprises: a secondpayload module, and a second overhead stowbin module structurallyintegrated with the second payload module and having a second stowagearea configured to receive stowbins, and at least one aisle supportstructure attached to the overhead payload module at one or morelocations along a length of the aisle floor assembly, wherein each aislesupport structure of the at least one aisle support structure comprises:a first support bracket having a first arm attached to the first payloadassembly and a second arm attached to the aisle floor assembly, a secondsupport bracket positioned opposite the first support bracket and havinga first arm attached to the second payload assembly and a second armattached to the aisle floor assembly, and a cross member having a firstend portion attached to the aisle floor assembly and the first supportbracket and having a second end portion attached to the aisle floorassembly and the second support bracket; and a support rail assemblypositioned within the fuselage and configured to support the overheadpayload module.
 9. The aircraft of claim 8, wherein the first overheadstowbin module comprises a first stowbin side wall, a first pair of endwalls, and a first center support wall that is attached to the firststowbin side wall between the first pair of end walls and that dividesthe first stowage area into two stowage areas each configured to receivestowbins, wherein the second overhead stowbin module comprises a secondstowbin side wall, a second pair of end walls, and a second centersupport wall that is attached to the second stowbin side wall betweenthe second pair of end walls and that divides the second stowage areainto two stowage areas each configured to receive stowbins.
 10. Theaircraft of claim 9, wherein the at least one aisle support structurecomprises two or more of: a first aisle support structure attached to afirst end wall of the first pair of end walls and a first end wall ofthe second pair of end walls, a second aisle support structure attachedto a second end wall of the first pair of end walls and a second endwall of the second pair of end walls, or a center aisle supportstructure attached to the first center support wall and the secondcenter support wall.
 11. The aircraft of claim 10, wherein the at leastone aisle support structure comprises the first aisle support structure,the second aisle support structure, and the center aisle supportstructure, and wherein the center aisle support structure is positionedsubstantially equidistant from the first aisle support structure and thesecond aisle support structure.
 12. The aircraft of claim 8, wherein thefirst payload assembly further comprises a first plurality ofsupplemental brackets attached to the first overhead stowbin module andto the aisle floor assembly, and wherein the second payload assemblyfurther comprises a second plurality of supplemental brackets attachedto the second overhead stowbin module and to the aisle floor assembly.13. The aircraft of claim 8, wherein the first payload module furthercomprises a first pair of side walls and a first pair of end walls,wherein the second payload module further comprises a second pair ofside walls and a second pair of end walls, wherein the first pair of endwalls are integrally formed with the first pair of side walls of thefirst payload module, and wherein the second pair of end walls areintegrally formed with the second pair of side walls of the secondpayload module.
 14. The aircraft of claim 8, wherein the first supportbracket includes a first stowbin pivot fitting integrally formed withthe first arm and the second arm of the first support bracket, whereinthe second support bracket includes a second stowbin pivot fittingintegrally formed with the first arm and the second arm of the secondsupport bracket, and wherein each stowbin pivot fitting of the firststowbin pivot fitting and the second stowbin pivot fitting defines anaxis about which a stowbin rotates when the stowbin is rotatablyattached to the stowbin pivot fitting.
 15. The aircraft of claim 8,further comprising a passenger service unit (PSU) support assemblyattached to the aisle floor assembly, wherein the PSU support assemblycomprises two side structures and an intermediate structure connectingthe two side structures, wherein the two side structures and theintermediate structure define a space configured to receive a PSU,wherein a distal end of one side structure of the two side structures isconfigured to couple to a hinge of the PSU and enable the PSU to rotateabout the hinge, and wherein a distal end of another side structure ofthe two side structures is configured to receive latches of the PSU forsecuring the PSU to the PSU support assembly.
 16. A method for balancingload in, and reinforcing an aisle structure of, an overhead payloadmodule of an aircraft, the method comprising: attaching a first payloadassembly to an aisle floor assembly to form a first side of the overheadpayload module, wherein the first payload assembly comprises: a firstpayload module, and a first overhead stowbin module structurallyintegrated with the first payload module and having a first stowage areaconfigured to receive stowbins; attaching a second payload assembly tothe aisle floor assembly to form a second side of the overhead payloadmodule, wherein the second payload assembly is positioned opposite thefirst payload assembly to form an aisle therebetween, wherein the secondpayload assembly comprises: a second payload module, and a secondoverhead stowbin module structurally integrated with the second payloadmodule and having a second stowage area configured to receive stowbins;attaching at least one aisle support structure to the overhead payloadmodule at one or more locations along a length of the aisle floorassembly, wherein attaching the at least one aisle support structure tothe overhead payload module comprises, for each aisle support structureof the at least one aisle support structure: attaching a first arm of afirst support bracket to the first payload assembly and a second arm ofthe first support bracket to the aisle floor assembly, attaching a firstarm of a second support bracket, positioned opposite the first supportbracket, to the second payload assembly and a second arm of the secondsupport bracket to the aisle floor assembly, and attaching a first endportion of a cross member to the aisle floor assembly and the firstsupport bracket and a second end portion of the cross member to theaisle floor assembly and the second support bracket.
 17. The method ofclaim 16, further comprising: attaching a first center support wall to afirst stowbin side wall of the first overhead stowbin module between afirst pair of end walls of the first overhead stowbin module to dividethe first stowage area into two stowage areas each configured to receivestowbins; and attaching a second center support wall to a second stowbinside wall of the second overhead stowbin module between a second pair ofend walls of the second overhead stowbin module to divide the secondstowage area into two stowage areas each configured to receive stowbins.18. The method of claim 17, wherein attaching the at least one aislesupport structure to the overhead payload module at the one or morelocations along the length of the aisle floor assembly comprises two ormore of: attaching a first aisle support structure to a first end wallof the first pair of end walls and a first end wall of the second pairof end walls, attaching a second aisle support structure to a second endwall of the first pair of end walls and a second end wall of the secondpair of end walls, or attaching a center aisle support structure to thefirst center support wall and the second center support wall.
 19. Themethod of claim 16, further comprising: attaching a first plurality ofsupplemental brackets to the first overhead stowbin module and to theaisle floor assembly; and attaching a second plurality of supplementalbrackets to the second overhead stowbin module and to the aisle floorassembly.
 20. The method of claim 16, further comprising: attaching apassenger service unit (PSU) support assembly to the aisle floorassembly, wherein the PSU support assembly comprises two side structuresand an intermediate structure connecting the two side structures,wherein the two side structures and the intermediate structure define aspace configured to receive a PSU, wherein a distal end of one sidestructure of the two side structures is configured to couple to a hingeof the PSU and enable the PSU to rotate about the hinge, and wherein adistal end of another side structure of the two side structures isconfigured to receive latches of the PSU for securing the PSU to the PSUsupport assembly.